Aeroplane



C. E. AND C. D STACY.

AEROPLANE.

APPLlCATlON FILED JUNE n. 1915.

Patented July 15, 1919.

2 SHEETSSHEET I IL! I ll I C. E. AND C. D. STACY.

AEROPLANE.

APPLICATION FILED JUNE 17. I916- ,309,968. Patented J 111 1919.

2 SHEETS T 2.

' awucmtoz 5 fi% art mama ml co., WASHINGTON n c 'rns PTENT OFFICE.

CHARLES E. STACY AND CORNELIUS D. STACY, 0F DAYTON, OHIO.

AEROPLAN E.

Specification of Letters Patent.

Patent ed July 15, 1919.

Application filed. June 17, 1916. Serial No. 104,148.

.county of Montgomery and State of Ohio,

have invented certain new and useful Improvements in Aeroplanes; and we'do declare the followinghto be a .full,fclear, and exact description of the invention, such as will enable others skilled in the art to which it appertains to make and use the same, reference being had to the accompanying drawings, and to the letters and figures of reference marked thereon, which form a part of this specification.

Our invention relates to certain improvements in air-planes commonly designated flying machines. The invention relates more specifically to means for controlling the direction of flight and for maintaining an inherent balance of the air-plane. The object of the invention is to provide an inherently stable air-plane and at the same time a means of control that does not add weight or head resistance to the machine when in flight. The balancing or self-righting properties of the machine are due to certain structural characteristics which involve the location and positions of two sub-planes which are located on Outriggers in the rear and at the ends of the main sustaining planes, as will hereinafter more fully appear from the following description in connection with the accompanying drawings.

In the accompanying drawings, Figure 1 is a top plan view .of our improved airplane, Fig. 2 is a front elevation thereof, Fig. 3 is a rear elevation thereof, Fig. 4: is an end elevation thereof.

For the purpose of adelineation of our invention, we show a common structure of main sustaining planes 1 and 2 which consists of any suitable fabric stretched upon a suitable light frame-work consisting of horizontal members 3 which are joined by struts 4 throughout their length and by which the two sustaining planes are maintained in position. At the ends of the main sustaining planes so united, out-riggers or frame members 5-5 and 6-6 are erected to extend rearwardly and to form triangular supporting frames or forks, the outward ends of which form bearings 77. As shown in Fig. 4, one of the bearings, to-wit, the inner main one at each end, lies above the other and said bearings are therefore arranged to support shafts 8 on angles substantially as shown in Figs. 2 and 3. The shafts 8' so arranged in the rear of the ends of the main planes form the axes of two sub-planes 99 which lie on angles substantially as shown in the drawings, wherein it will be seen that the sub-planes incline downwardly and outwardly. As shown in Figs. 1 and 4, these two sub-planes 9-9 are located a distance from the rear edge of the main planes so that there is a vacant space intervening between the rear edges of the main planes 1 and 2 and the front edges of the sub-planes. The centers of the sub-planes are as far in the rear of the center of gravity of the airplane as they are to the sides of the center of gravity, as shown by the aa lines, Fig. 1, in order to obtain the best efliciency. The downward angle or slant of the sub-planes toward the outer ends of the main planes should be about 30. By the downward and outward slant of the sub-planes a'certain perpendicular component results. This perpendicular component increases in its effect if the air crosses the main planes in other direction than from directly front to rear thus presenting more resistance and causing the machine to turn in the direction from which the air is coming. The effect is caused by virtue of the lever arm extending rearwardly from the center of gravity which is indicated by 13 in the drawings. By lever arm is meant the distance the center of pressure on the sub-planes is from the center of gravity, and the leverage obtained thereby. The above mentioned component is instrumental in controlling the perpendicular axis of the machine. In taking care of the longitudinal axis of the machine both subplanes are tilted simultaneously thus producing a fore and aft control. For taking care of the lateral balance of the machine, the sub-planes are tilted in opposite direction from each other. Inherent stability is possessed by the air-plane by virtue of the location and positions of the sub-planes. Should the machine side-slip the same corrective forces will come in to effect as would be the case if the aviator purposely arranged the sub-planes to turn the machine in that direction. This effect is caused by the particular mounting and positions of the subplanes. The sub-planes, mounted as described, provide safety means'and at the same time a steering control. Any suitable connection between the axes of the subplanes 9-9 and the operating levers 1010 of the machine may be provided.

with the sub-planes by means of suitable cables or wires 11 the ends of which are fixed to operating wheels 12 which are in turn mounted on the shafts 8 of the sub-planes.

WVhile we have described details with some minuteness we do not wish to be understood as indicating that these are vital arts'of the invention. The underlying principles of our invention reside in the two sub-planes and their locations and positions as described.

In the I drawings, the operating levers are connected Having described our invention we claim: In an air-plane, the combination with the main sustaining planes, of two sub-planes mounted in the rear of the ends of the main planes on downwardly and outwardly inclined axes, said sub-planes being arranged substantially as far in the rear of the center of gravity of the machine as to the side of the center of gravity.

In testimony whereof we affix our signatures, in presence of two witnesses.

CHARLES E. STACY. CORNELIUS D. STACY. Witnesses:

R. J. MCCARTY, MATTHEW SIEBLER.

Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents. Washington, D. 0. 

